Applications of multi-POD to a pitching and plunging airfoil
نویسندگان
چکیده
منابع مشابه
Unsteady flow past a plunging airfoil
This paper presents simulations of unsteady flow past a plunging airfoil using the highorder spectral difference (SD) method. Both third-order and fourth-order SD methods are used on unstructured quadrilateral grids. The vortex shedding pattern of an airfoil in an oscillating plunge motion becomes asymmetric at a sufficiently high frequency. The SD method is able to capture this effect and reve...
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This paper describes the application of the noncommercial CFD-code FLOWer to the problem of a sinusoidally pitching NACA 0012 airfoil with high amplitude and reduced frequency under incompressible flow conditions. As FLOWer allows the approximate solution of the nonlinear conservation laws governing viscous fluid flow, i. e. the Navier-Stokes equations, a numerical investigation of the unsteady...
متن کاملAerodynamics of Low Reynolds Number Plunging Airfoil under Gusty Environment
Abstract It is known that plunging airfoil can produce both lift and thrust with certain combination of plunging amplitude and frequency. Motivated by our interest in micro air vehicles (MAVs), we utilize a NavierStokes equation solver to investigate the aerodynamics of a flapping airfoil. The roles of the plunging and pitching amplitude and frequency, and Strouhal number are studied. For a sym...
متن کاملSimulation of Pitching and Heaving Airfoil with Oscillation of Flow Boundary Condition
A pressure based implicit procedure to solve the Euler and Navier-Stokes equation is developed to predict transonic viscous and inviscid flows around the pitching and heaving airfoils with a high reslution scheme. In this process, nonorthogonal and non moving mesh with collocated finite volume formulation are used. In order to simulate pitching or heaving airfoil, oscillation of flow boundary c...
متن کاملPlunging Airfoil Load Characteristics Equipped with Gurney Flap
Numerous experiments have been conducted on plunging Eppler 361 airfoil in a subsonic wind tunnel. The experimental tests involved measuring the surface pressure distribution over the airfoil at Re=1.5×105. The airfoil was equipped with Gurney flap(heights of 2.6, 3.3 and 5% chord) and plunged at 6cm amplitude. The unsteady aerodynamic loads were calculated from the surface pressure measurement...
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ژورنال
عنوان ژورنال: Mathematical and Computer Modelling
سال: 2005
ISSN: 0895-7177
DOI: 10.1016/j.mcm.2005.06.003